FSI Analysis of trailing edge region cooling in hp stage turbine blade

Kamat, Harishkumar and Kini, Chandrakant R and Sharma, Yagnesh N (2017) FSI Analysis of trailing edge region cooling in hp stage turbine blade. In: International conference on mechanical and aeronautical engineering, 18/01/2017, Bangkok, Thailand, Jan 18-19, 2017.

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Abstract

Gas turbines play a vital role in the today’s industrialized society, and as the demands for power increase, the power output and thermal efficiency of gas turbines must also increase. Modern high-speed aero-engines operate at elevated temperatures about 2000 K to achieve better cycle efficiencies. The internal cooling techniques of the gas turbine blade includes: jet impingement, rib turbulated cooling, and pin-fin cooling which have been developed to maintain the metal temperature of turbine blades within acceptable limits. Since FSI is the objective of this analysis, the blade loading corresponding to the static pressure as well as temperature field on the blades surfaces are obtained using CFD run. The output results are then used as structural boundary condition to solve FSI, using finite element method. The present work brings out thermal and structural deformation of the HP stage gas turbine blade. A parametric approach is used for varying the cooling duct geometry to optimize the cooling process. It is found from the FSI analysis that cooling passages having pin fins and aerofoil fins in the trailing edge region achieve maximum thermal performance in terms of cooling and in turn reduce structural distortion.

Item Type: Conference or Workshop Item (Paper)
Uncontrolled Keywords: FSI analysis, Fins, Trailing edge cooling, blade deformation
Subjects: Engineering > MIT Manipal > Aeronautical and Automobile
Engineering > MIT Manipal > Mechanical and Manufacturing
Depositing User: MIT Library
Date Deposited: 13 Feb 2017 10:45
Last Modified: 13 Feb 2017 10:48
URI: http://eprints.manipal.edu/id/eprint/148297

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